B A Naca 6412 Aerofoil Is Shown In The Figure Below Figure Q1b Not To Scale Assuming An Aircraft Using A Naca 6412 G 1 (119.88 KiB) Viewed 31 times
(b) A NACA 6412 aerofoil is shown in the figure below Figure Q1b – not to scale Assuming an aircraft using a NACA 6412 geometry has a wing chord of 3.25m, determine; (i) The maximum camber [1] (ii) The position of maximum camber relative to the leading edge [1] (iii) The maximum thickness [1] (iv) The camber value 1m from the leading edge [3]
(b) A NACA 6412 aerofoil is shown in the figure below Figure Q1b – not to scale Assuming an aircraft using a NACA 6412 geometry has a wing chord of 3.25m, determine; (i) The maximum camber [1] (ii) The position of maximum camber relative to the leading edge [1] (iii) The maximum thickness [1] (iv) The camber value 1m from the leading edge [3]
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